JPH1198777A - Rotor using titanium alloy and manufacture thereof - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a rotor and its manufacture method which improves effective utilization factor of an expensive material such as a titanium alloy, attaining reduction in work cost and improvement in the yield of the material, and is high strength and low in inertia. SOLUTION: In this method of manufacture, a titanium alloy large thickness cylinder 11 is plastically worked by a super plastic gas pressure molding method into a different diameter cylindrical member provided with a shaft part 11b and a rotor peripheral part reinforced ring 11a, in the reinforced ring 11a, a high energy product rate-earth magnet and a core material or the like are housed, in a rotor using a titanium alloy. In a different diametric cylinder member concurrently provided with a structure of shat part 11b and rotor peripheral part reinforced ring 11a of the titanium alloy large thickness cylinder 11 by the super plastic gas pressure molding method, plastic work is applied.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention applies a superplasticity phenomenon of a titanium alloy to plastically process a titanium alloy in a cylindrical shape, and incorporates various kinds of rare earth magnets or iron core materials in a rotor portion. The present invention relates to a rotor using a titanium alloy having inertia and a method for manufacturing the same.

[0002]

2. Description of the Related Art An example of a schematic structure of a rotor employed in a conventionally known permanent magnet high-speed generator or electric motor will be described with reference to FIGS. 20A and 20B. The shaft 2 is a rare earth magnet, 3 is a metal cylinder made of a non-magnetic material, and 4 and 4 are metal disks made of a non-magnetic material.

In this rotor structure, the strength of the rare earth magnet 2
For example, since the tensile strength, bending strength, and torsional strength are low and the rigidity is low, the metal discs 4 are shrink-fitted at both ends of the metal cylinder 3 using a non-magnetic metal material such as austenitic stainless steel, so that the internal Is held by the metal cylinder 3 and the metal disk 4 to maintain the strength and rigidity of the rotor.

Further, in the conventional example shown in FIGS. 21A and 21B, a core 5 made of a bulk material or a laminated material is provided around the shaft 1.
And a plurality of wedge-shaped core grooves 6 are formed in a peripheral portion of the iron core 5 along the longitudinal direction.
Means are provided in which the rare earth magnets 2 and 2 are disposed and bonded using a polymer adhesive such as an epoxy resin. Further, the rare earth magnet 2 is restrained by using a fiber reinforced plastic material (FRP) reinforced with an aramid fiber (Kevlar) or a glass fiber together with the metal cylinder 3 in the outer circumferential direction, together with the hoop reinforcement, At present, a rotor that can withstand high-speed rotation is realized.

The rare earth magnet 2 may be an Nd—Fe—B magnet using neodymium or a Pd using praseodymium.
Sm-Co using r-Fe-B based magnet and samarium
It is a magnet having a high magnetic energy product containing an active rare earth element as a main component, such as a system magnet, and since the rare earth magnet 2 is easily corroded, it is subjected to an epoxy coating, an aluminum chromate film or a nickel plating of a copper base, and the like.
For fixing to the metal of the rotor member such as the metal cylinder 3, a means for bonding using a polymer adhesive such as an epoxy resin is employed.

[0006]

With the advent of the rare earth magnets described above, the magnetic properties have been dramatically improved. In a permanent magnet type synchronous machine incorporating these powerful magnets in a rotor, an induction machine or a winding As compared with the synchronous machine, the energy density per unit area is higher and the rotational speed can be increased, so that the output can be improved, and further, there is an advantage that the motor and the generator can be reduced in size and higher in performance. However, there are the following problems.

First, the rare earth magnet produced by the powder sintering method is essentially a brittle material, and has mechanical strength, rigidity, toughness, deformability, etc., as compared with the iron core and other metal materials constituting the rotor. When the centrifugal force acting on the rotor is further increased due to the high speed or large capacity of the electric motor or the like, the deformation or breakage of the rare earth magnet is liable to occur due to the lack of mechanical characteristics.

For example, rare earth magnets are manufactured by means such as a powder sintering method, a forging method, and a rolling method.
The B-based magnet is manufactured by a hot press method of the super-quenched magnet powder or a hot plastic working method of the super-quenched magnet powder.
The bending strength of the d-Fe-B-based magnet is about 260 (MPa), which is less than half that of ordinary steel, and the elastic modulus is about 15
0 (GPa), which is about ／ of steel.

Further, the elongation at break is about 0.2%, which is 1/10 that of steel.
Below, it is extremely small, and has been broken only by elastic deformation with little plastic deformation. However, the compression strength is more than twice as large as the bending and tensile strength. The Pr-Fe-B based magnet has almost the same strength as this, but the strength of the Sm-Co based magnet is much smaller.

[0010] One of the factors that reduce the strength of the powder sintered magnet is internal defects such as voids and minute cracks contained in the powder sintered magnet in an argon gas atmosphere at normal pressure or slightly reduced pressure. Is considered possible.

Second, the corrosion resistance of the rare earth magnet is insufficient. The Nd-Fe-B system, Pr-Fe
In each of the -B-based and Sm-Co-based rare-earth magnets, neodymium, praseodymium, and samarium, which are one of the constituent elements, are active. Therefore, the surface of these rare-earth magnets is discolored when left in the air for several days. And corrosion progresses. Therefore, it is usually put to practical use in a state where an epoxy coating, an aluminum chromate treatment or a nickel plating of a copper base is applied.

Third, there is insufficient bonding strength between the rare earth magnet and the rotor member metal. For example, the tensile strength of a rare earth magnet joined with an epoxy resin agent and a rotor member metal, for example, steel, is about 20 (MPa) at room temperature, which is Nd-F
It is about 1/4 of the tensile strength of the eB magnet. In addition, the bonding strength is further reduced at a high temperature exceeding 100 ° C., so that almost no bonding strength can be expected in a rotor portion which generates heat at 100 ° C. or more during operation. In addition, normal N
When using d-Fe-B magnets, the maximum heat resistance is 140 to 1
It is 60 ° C.

Fourth, a high-strength joining technique that does not deteriorate the magnetic properties of the rare-earth magnet has not been established. That is, 100 ° C. without deteriorating the original magnetic properties of the rare earth magnet.
At present, a high-strength joining technique between a magnet and a metal of a rotor member that can withstand the heat generation temperature of the rotor exceeding the above limit has not been established. Since the rare earth element is extremely active as described above, even if an attempt is made to braze the rare earth magnet and the rotor member metal at a high temperature of about 850 to 900 ° C. with a metal brazing material such as silver brazing, the rare earth element and the brazing material are It is extremely difficult to join the magnets without reacting violently and deteriorating the magnetic properties of the magnets, and the joining strength is 10 (MPa) or less. Further, in the Nd-Fe-B magnet, there is a problem that the silver element in the brazing material diffuses deep inside the magnet, and the coercive force of the magnet is greatly reduced.

As described above, by shrink-fitting both ends of the metal cylinder 3 using a non-magnetic metal material, the rare earth magnet 2 inside is restrained by the metal cylinder 3 and the metal disk 4, and withstands high centrifugal force. In order to realize a rotor with low inertia,
It is desirable to use a high specific strength metal material having high strength and low specific gravity.

The nonmagnetic metal-based material having the maximum specific strength is a titanium alloy for mechanical structure. Generally, this titanium alloy is supplied as a solid cylindrical hot forging material at the distribution stage. Moreover, titanium alloys are expensive in price, and because they are hard-to-cut materials with active metals, the processing cost for machining the solid cylindrical hot forged material into a thin-walled cylindrical reinforcing ring increases. There is a problem that the yield of the material, that is, the effective utilization rate of the expensive material is reduced.

Accordingly, the present invention has been made in view of the above, and is intended to reduce the processing cost and improve the material yield by using a titanium alloy for a mechanical structure which is a non-magnetic metal-based material. It is an object of the present invention to provide a rotor having high strength and low inertia while increasing the effective utilization rate of a material, and a method for manufacturing the same.

[0017]

SUMMARY OF THE INVENTION In order to achieve the above object, the present invention provides a method for forming a thick titanium alloy cylinder into a cylindrical member having a shaft portion and a rotor outer peripheral reinforcing ring by superplastic gas pressure molding. A rotor using a titanium alloy with a high-energy product rare earth magnet or an iron core material built in the rotor outer peripheral reinforcing ring inside the rotor, and a titanium alloy thick cylinder by a superplastic gas pressure forming method. Basically, a rotor is manufactured using a titanium alloy with plastic working on a different-diameter cylindrical member that also has the structure of the outer circumferential reinforcing ring and a high-energy product rare earth magnet or iron core material built into the outer circumferential reinforcing ring of the rotor. Means.

In the superplastic gas pressure forming method, a titanium alloy cylinder is inserted and fixed inside a mold, and a high-temperature and high-pressure inert gas is introduced into the mold while heating the titanium alloy cylinder with a heater. By performing a pressure treatment from inside the metal cylinder, the titanium metal cylinder is subjected to superplastic gas pressure forming to be formed into a cylindrical shape having a shaft portion and a rotor outer peripheral reinforcing ring.

The titanium metal cylinder is "Ti-4.5Al-3".
The processing conditions for superplastic gas pressure forming in the case of “V-2Fe-2Mo” alloy include a forming temperature of 780 ° C. ± 50 ° C., a strain rate of 1 × 10 ⁻² / s or less, and an inert gas pressure of 20 ° C.
Up to 120 MPa, and the titanium metal cylinder is made of “Ti-6Al
The processing conditions for superplastic gas pressing in the case of a “-4V” alloy include a forming temperature of 880 ° C. ± 50 ° C. and a strain rate of 1 ×
10 ^-2 / s or less, inert gas pressure is 20 to 120MPa
a.

As a specific manufacturing method, a cylindrical member formed of a shaft portion and a rotor outer peripheral reinforcing ring formed by superplastic gas pressure forming is cut into two parts in the circumferential direction at the reinforcing ring portion. After that, a rare-earth magnet is placed on both sides of the titanium alloy disk in the reinforcing ring in combination, and the cylindrical members of different diameters are heated to a high temperature and fired while applying an axial compressive load to both ends of the shaft. Fit the butt of the reinforcing ring with no gap, and then rotate the butt of the reinforcing ring and the titanium alloy disc over the entire circumference by electron beam welding while rotating while applying a compressive load in the axial direction. A method of integrally joining is adopted.

Further, in the reinforcing ring, a rare-earth magnet and a non-magnetic shaft are combined on both sides around the titanium alloy disk, and an iron core is placed on both sides around the titanium alloy disk inside the reinforcing ring. An example is provided in which a rare earth magnet is inserted and constrained in an iron core groove provided along the longitudinal direction of the peripheral edge of the iron core, and a method using a two-layer solid shaft as the iron core.

As the iron core, a bulk material made of a ferromagnetic material such as pure iron, low carbon steel, low alloy steel, or the like, or a laminated material in which silicon steel plates are laminated is used.

An iron core is pressed into a ferromagnetic shaft centering on a titanium alloy disk in the reinforcing ring, and a rare earth magnet is inserted and restrained in an iron core groove provided along the longitudinal direction of the peripheral edge of the iron core. To provide a way. A grooved ferromagnetic shaft or an aluminum die-cast shaft is used as the ferromagnetic shaft.

Further, a method of arranging magnetic end plates on both sides around the rare earth magnet in the reinforcing ring, a method of arranging an odd number of divided rare earth magnets in the reinforcing ring, and a method of laminating in the reinforcing ring. The present invention provides a method in which a mold core is press-fitted into a ferromagnetic shaft, and a rare earth magnet is inserted into and constrained in a core groove provided along the longitudinal direction of the periphery of the core.

As the non-magnetic metal cylinder, an aluminum alloy,
Use non-magnetic metal materials such as titanium alloy, austenitic stainless steel, and high manganese steel machined members.

As a superplastic gas pressure forming method, an inert gas introduction pipe is connected to one side of the mold, a gas reservoir tank is provided on the other side of the mold, and a titanium alloy cylinder is inserted and fixed inside the mold. Then, while heating the titanium alloy cylinder with a heater, a high-temperature and high-pressure inert gas is introduced into the mold from the inert gas introduction pipe into the mold, and a pressurizing process is performed from the inside of the titanium metal cylinder to form a shaft portion and a rotor outer peripheral portion. It is based on a method of forming into a cylindrical shape having a different diameter composed of a reinforcing ring.

Further, as a superplastic gas pressure molding method, a method in which a lid member is provided on the other side of the mold and the mold is closed, and an inert gas introduction pipe is provided on one side and the other side of the mold, and the mold is provided from both sides. A method of introducing a high-temperature and high-pressure inert gas into the inside and a method of forming a titanium alloy bellows by providing a corrugated groove on the inner diameter side of a mold are used.

According to the rotor using the titanium alloy and the method of manufacturing the same, a high-temperature and high-pressure argon gas is introduced into the mold as an inert gas from a gas tank to serve as a pressure medium, and the titanium metal cylinder is heated by a heater. By applying a predetermined pressure, the titanium metal cylinder is pressurized from the inside and subjected to superplastic gas pressure forming, whereby the titanium metal cylinder can be formed into a cylindrical member having a different diameter comprising a shaft portion and a rotor outer peripheral portion reinforcing ring.

After being cut into two parts in the circumferential direction at the rotor outer peripheral reinforcing ring portion of the different diameter cylindrical member, a titanium alloy disk, a rare earth magnet, a non-magnetic end plate, a ferromagnetic shaft and a non-magnetic A magnetic metal cylinder is combined and arranged, and shrink-fit is performed while applying a compressive load in the axial direction to both ends of the shaft while heating. Either joint the butted part of the reinforcing ring and the titanium alloy disk together over the entire circumference by electron beam welding while rotating while applying a load, or shrink fit a non-magnetic metal cylinder from the outer circumference of the reinforcing ring part Thus, a rotor using a titanium alloy is obtained.

[0030]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Various embodiments of a rotor using a titanium alloy according to the present invention and a method for manufacturing the same will be described below. The present invention applies the superplasticity phenomenon of titanium alloy to the superplastic gas pressure forming method, and uses a titanium alloy thick cylinder with uniform inner and outer diameters to form a different diameter cylinder having a structure of a shaft part and a rotor outer peripheral reinforcing ring. The basic means is to obtain a high-strength, low-inertia rotor in which a high-energy product rare-earth magnet, an iron core material, and the like are incorporated in a rotor portion after plastic working is performed.

The above-mentioned "superplastic gas pressing" means that a metal material maintains a low deformation stress, that is, a flow stress under a special condition, and has several hundreds to several hundreds of necks without necking.
A phenomenon that extends to more than 1,000%.

In the metal structure of the titanium alloy, the β phase (body-centered cubic) has more sliding directions than the α phase (closest hexagonal). It is valid. Therefore, recently, attention has been paid to a β alloy in which the α phase, which is a main factor of the difficult workability of the α + β alloy, has been eliminated or reduced, and a “near β alloy” having a large amount of β stabilizing elements even in the α + β alloy.

On the other hand, a recent steel maker pays attention to the superplasticity phenomenon of a titanium alloy, and obtains a “Ti-4.5Al-3V-2Fe-2Mo” alloy (near β alloy: SP) capable of obtaining superplasticity at a temperature as low as possible. -700). The feature of this alloy is that a “Ti-6Al-4V” alloy (α + β) which has been widely used in aircraft and the like as a titanium alloy for mechanical structures.
Alloy), superplasticity is obtained at about 780 ° C., which is lower by about 100 ° C., and the amount of β-stabilizing element is large, and workability is improved.

Table 1 shows "Ti-4.5Al-3V-2F".
e-2Mo "and" Ti-6Al-4V "alloys, the chemical compositions of which are shown in FIG.
3 shows temperature characteristics of elongation at break and flow stress (deformation stress) of both titanium alloys obtained in a tensile test at a strain rate of 3 × 10 ⁻³ / S at m.

[0035]

[Table 1]

The "Ti-6Al-4V" alloy is approximately 400% at around 880 ° C., and “Ti-4.5Al-3V-2Fe-
The "2Mo" alloy has a very large plastic elongation of about 2500% around 780 ° C., and in such a temperature range, both titanium alloys show a small flow stress of about 50 MPa or less.

Accordingly, the present invention is to develop a thick inner cylinder having a uniform inner and outer diameter in a mold, which is made of an expensive titanium alloy which is a high specific strength material but is an active metal and which is difficult to cut, and exhibits superplasticity in a mold. Heating and holding in the high temperature area, blowing high-temperature and high-pressure argon gas into the inner diameter part, and expanding and deforming the central part of the cylinder from the inner diameter side at a low strain rate, thereby combining the structure of the shaft part and the rotor outer peripheral part reinforcing ring. It is characterized in that it is superplastically processed into a different diameter cylinder and used as a material for a rotor.

FIGS. 1 and 2 are schematic views showing a first embodiment of the present invention. FIG. 1 shows a cross-sectional shape of a titanium alloy cylinder before gas pressure forming, and FIG. 2 shows a cross-sectional shape of a titanium alloy cylinder after pressure forming. In addition, the receiving material of the titanium alloy which is a solid cylindrical material is machined in advance into a thick cylindrical shape.

In the figure, reference numeral 11 denotes a thick-walled cylindrical titanium alloy cylinder to be subjected to superplastic working, 12, 13 a vertically divided two-piece mold for holding the titanium alloy cylinder 11, 14 a gas storage tank, 15 is a pipe for supplying high-temperature and high-pressure argon gas from a large-capacity gas tank (not shown) via a valve; 16 is a heater for heating the titanium alloy cylinder 11 through two-piece molds 12 and 13; 17 is a heat insulating layer; , 9 are water cooling pipes.

After the titanium alloy cylinder 11 is inserted into the inside of the two-piece molds 12 and 13, the flanges 12 a and 12 a at both ends of the cylinder 12 are respectively inserted.
12b and 13a, 13b are connected to a flange portion 15a of a pipe 15 for supplying high-pressure argon gas and a gas storage tank 1
4 is fixed to the flange portion 14a by bolting. The water cooling pipes 8 and 9 are divided into two molds 12 and
13 and for cooling the flange portions 12a, 12b, 13a, 13b and the titanium alloy cylinder 11.

Since the gas storage tank 14 is provided, a pressing force is applied not only from the supply side of the high-temperature and high-pressure argon gas but also from the gas storage tank 14 side during the gas pressure molding, so that the titanium alloy cylinder 11 is A uniform internal pressure can be given.

In practice, a high-temperature and high-pressure argon gas as an inert gas is introduced from a large-capacity gas tank (not shown) through a pipe 15 to serve as a pressure medium. Pressure and temperature, and a superplastic gas pressure forming process is performed on the titanium metal cylinder 11 by performing a pressure treatment from the inside of the titanium metal cylinder 11 as shown by an arrow p in FIG. 11 is formed into a cylindrical shape having different diameters composed of shaft portions 11b, 11b and a rotor outer peripheral portion reinforcing ring 11a.

The processing conditions of the superplastic gas pressure forming process are as follows: the titanium metal cylinder 11 is "Ti-4.5Al-3V-2Fe-
In the case of a “2Mo” alloy (near β alloy: SP-700), the molding temperature is 780 ° C. ± 50 ° C., and the strain rate is 1 ×
10 ⁻² / s or less, preferably 5 × 10 ⁻³ / s or less. The pressure of argon gas as an inert gas is 20
To 120 MPa. The pressure of the argon gas needs to be set within a range that satisfies the strain rate condition.

The titanium metal cylinder 11 is made of "Ti-6Al-4".
In the case of V "alloy (α + β alloy), the molding temperature is 880 ° C
The temperature is set to ± 50 ° C., and the strain rate is set to 1 × 10 ⁻² / s or less, preferably 5 × 10 ⁻³ / s or less. The pressure of the argon gas is set to 20 to 120 MPa. The pressure of this argon gas needs to be set within a range that satisfies the strain rate condition.

The obtained cylindrical member composed of the shaft portions 11b, 11b and the outer peripheral portion reinforcing ring 11a is cut into two parts in the circumferential direction at the portion of the reinforcing ring 11a, and a rotor as described below is assembled. Provide to the process.

FIGS. 3A and 3B are schematic diagrams of a rotor structure (a) showing a second embodiment of the present invention.
1b is a titanium alloy cylinder 1 obtained by dividing the different diameter cylindrical member obtained by the apparatus of FIG.
Reference numeral 1 denotes a shaft portion, 11a denotes the same reinforcing ring, 18 denotes a titanium alloy disk, 2, 2 denotes a rare earth magnet, and 19 denotes an electron beam welding portion for joining a titanium alloy cylinder. The manufacturing process will be briefly described below. (1) A titanium alloy disc 18 is combined between the rare earth magnets 2 and 2 to form a titanium alloy cylinder reinforcing ring 11.
a) heating the titanium alloy cylinder 11 having a different diameter to a high temperature of about 300 ° C. to 350 ° C.
b and 11b are shrink-fitted with an axial compressive load applied to both ends, and (3) the reinforcing ring 11 of the titanium alloy cylinder 11
The clearance is set so that there is almost no gap at the abutting portion (a) (clearance is 0.3 mm or less). (4) The shaft portions 11b and both ends of the titanium alloy cylinder 11 are sandwiched between chucks of a rotating jig (not shown). The butting portion of the reinforcing ring 11a and the titanium alloy disk 18 are integrally joined over the entire circumference by the electron beam welding portion 19 while rotating while slightly applying a compressive load in the axial direction.

During the above steps, the electron beam weld 19 is formed by a welding operation in a vacuum atmosphere, and the degree of vacuum at this time is 1
It is preferable to set the high vacuum of × 10 ^-1 Pa or more, for example, 1 × 10 ^-2 Pa or more.

As described in the first and second embodiments, a step of machining a solid cylindrical receiving material into a thick cylindrical titanium alloy cylinder 11 and a step of performing superplastic processing. Except for the cutting step of dividing the obtained different-diameter cylindrical member into two parts in the circumferential direction by the reinforcing ring 11a at the center of the rotor part, the subsequent cutting step is omitted, so that the number of machining steps in manufacturing the rotor is greatly reduced. Thus, the cost and the yield of the material, that is, the effective utilization rate of the expensive material can be improved, and the cost can be greatly reduced.

Further, by forming the shaft portion 11b and the rotor outer peripheral reinforcing ring 11a as an integral member, the number of parts as a rotor is reduced, and the shaft portion 11b and the reinforcing ring 11a are reduced.
The parts can have high specific strength and light weight, and the rotor can be downsized, high performance, and low inertia.

FIGS. 4A, 4B and 4C are schematic views of a rotor structure (b) showing a third embodiment of the present invention.
b and 11b are shaft parts of a titanium alloy cylinder divided into two parts, 11a is the same reinforcing ring, 20 and 20 are non-magnetic shafts,
Reference numeral 18 denotes a titanium alloy disk, reference numerals 2 and 2 denote rare earth magnets, and reference numeral 19 denotes an electron beam weld. For the non-magnetic shafts 20, 20, use is made of a non-magnetic metal material of a two-layer solid shaft such as an aluminum alloy hot forged product, a titanium alloy, an austenitic stainless steel, or a high manganese steel machined member. The manufacturing process will be briefly described. (1) The non-magnetic shafts 20, 20, the rare-earth magnets 2, 2, and the titanium alloy disk 18 are combined as shown in the figure and placed in the reinforcing ring 11a of the titanium alloy cylinder 11, (2) Titanium alloy cylinder 11 is heated at about 300 ° C. to 350 ° C.
C. and then shrink-fitted with an axial compressive load applied to both ends of the shaft portions 11b, 11b so that (3) almost no gap is formed at the butting portion of the reinforcing ring 11a of the titanium alloy cylinder 11. (4) Titanium alloy cylinder 1
The two ends of the shaft portions 11b, 11b are sandwiched between chucks of a rotary jig, and while rotating under a slight compressive load in the axial direction, the butted portion of the reinforcing ring 11a and the titanium alloy circle are rotated by the electron beam welding portion 19. The plate 18 and the entire periphery are integrally joined.

FIGS. 5A and 5B are schematic diagrams of a rotor structure (c) showing a fourth embodiment of the present invention.
1b is a shaft portion of the titanium alloy cylinder 11, 11a is the same reinforcing ring, 5 and 5 are iron cores made of bulk material, 6 and 6 are iron core grooves, 18 is a titanium alloy disk, 2, 2 is a rare earth magnet, 19
Is an electron beam weld. As the bulk material of the iron cores 5, 5, a ferromagnetic material such as pure iron or low carbon steel or low alloy steel is used. The manufacturing process will be briefly described. (1) Inserting the rare-earth magnets 2, 2 into wedge-shaped core grooves 6, 6 provided along the longitudinal direction on the peripheral edges of the cores 5, 5 made of bulk material. Mechanically constrained, (2) the titanium alloy disk 18 is placed in the reinforcing ring 11a of the titanium alloy cylinder 11 between the iron cores 5 and 5;
(3) Heating to a high temperature of 50 ° C. and shrink-fitting while applying an axial compressive load to both ends of the shaft portions 11b, 11b
(4) The both ends of the shaft portions 11b and 11b of the titanium alloy cylinder 11 are sandwiched between chucks of a rotating jig, and slightly set in the axial direction. While rotating under a compressive load, the reinforcing ring 11 is
The butted portion (a) and the titanium alloy disk 18 are integrally joined over the entire circumference.

FIGS. 6A and 6B are schematic views of a rotor structure (d) showing a fifth embodiment of the present invention.
1b is a shaft portion of the titanium alloy cylinder 11, 11a is the same reinforcing ring, 5 and 5 are iron cores composed of a two-layer solid shaft made of a bulk material, 6 and 6 are iron core grooves, 18 is a titanium alloy disk, 2 , 2 are rare earth magnets and 19 is an electron beam weld. The manufacturing process is substantially the same as that of the fourth embodiment.

The fifth embodiment is an example in which rigidity is further increased as compared with the fourth embodiment by using two-layer solid shafts as the iron cores 5 and 5.

FIGS. 7A, 7B and 7C are schematic views of a rotor structure (e) showing a sixth embodiment of the present invention.
b, 11b are shaft portions of the titanium alloy cylinder 11, 11a
Is the reinforcing ring, 5, 5 is an iron core made of a laminated material, 6, 6 is an iron core groove, 18 is a titanium alloy disk, 2, 2 is a rare earth magnet, 1
9 is an electron beam welding part. As a laminated material of the iron cores 5, 5, a silicon steel plate, for example, a 6.5% high silicon steel plate is laminated and used. The manufacturing process is substantially the same as that of the fourth embodiment.

FIGS. 8A, 8B and 8C are schematic views of a rotor structure (f) showing a seventh embodiment of the present invention.
b, 11b are shaft portions of the titanium alloy cylinder 11, 11a
Is the reinforcing ring, 21 is a ferromagnetic shaft, 5 and 5 are iron cores made of a laminated material, 6 and 6 are iron core grooves, 18 is a titanium alloy disk,
Reference numerals 2 and 2 denote rare earth magnets, and 19 denotes an electron beam weld.
The manufacturing process will be briefly described. (1) The iron cores 5 and 5 made of a laminated material and the titanium alloy disk 18 are pressed into the ferromagnetic shaft 21 and arranged in the reinforcing ring 11 a of the titanium alloy cylinder 11.
(2) The rare earth magnets 2, 2 are inserted into the wedge-shaped iron core grooves 6, 6 provided along the longitudinal direction on the periphery of the iron cores 5, 5, and are mechanically restrained. (3) Titanium alloy cylinder 11 to a high temperature of about 300 ° C. to 350 ° C.
b and 11b are shrink-fitted with an axial compressive load applied to both ends, and (4) the titanium alloy cylinder 11 is set so that there is almost no gap at the butting portion of the reinforcing ring 11a,
(5) Shaft portions 11b, 11b of titanium alloy cylinder 11
Both ends are sandwiched between chucks of a rotary jig, and the butted portion of the reinforcing ring 11a and the titanium alloy disk 1 are rotated by the electron beam welding portion 19 while rotating while applying a slight compressive load in the axial direction.
And 8 are integrally joined over the entire circumference.

FIGS. 9A, 9B and 9C are schematic views of a rotor structure (g) showing an eighth embodiment of the present invention.
b, 11b are shaft portions of the titanium alloy cylinder 11, 11a
Is the reinforcing ring, 21a is a grooved ferromagnetic shaft, 22, 2
2 is a key fitted and fixed in the groove, 5, 5 is an iron core made of a laminated material, 6, 6 is an iron core groove, 18 is a titanium alloy disk, 2,
2 is a rare earth magnet, 23 and 23 are non-magnetic end plates, and 19 is an electron beam weld. Aluminum alloys or titanium alloys, austenitic stainless steel,
Use a non-magnetic metal material such as a high manganese steel machined member. The manufacturing process will be briefly described. (1) The key 22 is attached to the groove of the grooved ferromagnetic shaft 21a, and the iron cores 5 and 5 made of a laminated material, the titanium alloy disk 18, the non-magnetic end plate 23,
23 are press-fitted into the grooved ferromagnetic shaft 21a, and (2) the rare earth magnets 2, 2 are inserted into the wedge-shaped core grooves 6, 6 provided along the longitudinal direction on the periphery of the iron cores 5, 5.
(3) Titanium alloy cylinder 11
Is heated to a high temperature of about 300 to 350 ° C.
1b and 11b are shrink-fitted with an axial compressive load applied to both ends thereof. (4) The titanium alloy cylinder 11 is set so that there is almost no gap at the butting portion of the reinforcing ring 11a.
(5) Shaft portions 11b, 11b of titanium alloy cylinder 11
Both ends are sandwiched between chucks of a rotary jig, and the butted portion of the reinforcing ring 11a and the titanium alloy disk 1 are rotated by the electron beam welding portion 19 while rotating while applying a slight compressive load in the axial direction.
And 8 are integrally joined over the entire circumference.

FIGS. 10A, 10B and 10C show a ninth embodiment of the present invention.
FIG. 3 is a schematic diagram of a rotor structure (h) showing an embodiment example,
1b and 11b are shaft portions of the titanium alloy cylinder 11;
a is the same reinforcing ring, 24 is an aluminum die-cast shaft,
Reference numerals 5 and 5 are iron cores made of a laminated material, 6 and 6 are iron core grooves, 18 is a titanium alloy disc, 2 and 2 are rare earth magnets, and 19 is an electron beam welded portion.

This embodiment is characterized in that the hollow portions of the titanium alloy cylinders 11, 11 are filled with an aluminum alloy by an aluminum die-cast shaft 24 to improve rigidity. The manufacturing process is substantially the same as that of the eighth embodiment.

FIGS. 11A, 11B and 11C show the first embodiment of the present invention.
FIG. 7 is a schematic diagram of a rotor structure (i) showing a zeroth embodiment;
11b, 11b are shaft portions of the titanium alloy cylinder 11, 1
1a is the reinforcing ring, 2 is a rare earth magnet, 23 and 23 are non-magnetic end plates, and 25 is a non-magnetic metal cylinder. Non-magnetic metal cylinder 2
5 is made of a non-magnetic metal material such as an aluminum alloy, a titanium alloy, an austenitic stainless steel, or a high-manganese steel machined member. The manufacturing process will be briefly described. (1) The rare earth magnet 2 is combined between the non-magnetic end plates 23 and 23 and disposed in the reinforcing ring 11a of the titanium alloy cylinder 11, and (2) the titanium alloy cylinder 11 is heated to about 300 ° C. The non-magnetic metal cylinder 25 is shrunk from the outer periphery of the reinforcing ring 11a in a state where the non-magnetic metal cylinder 25 is heated to a high temperature of about 350 ° C. and an axial compressive load is applied to both ends of the shaft portions 11b. (3) Both ends of the shaft portions 11b, 11b of the titanium alloy cylinder 11 are sandwiched between chucks of a rotating jig, and rotated while slightly applying a compressive load in the axial direction. While joining together.

This embodiment is characterized in that electron beam welding is unnecessary because the titanium alloy disk 18 used in each of the above embodiments is not used.

FIGS. 12A, 12B and 12C show the first embodiment of the present invention.
It is a schematic diagram of a rotor structure (j) showing one embodiment,
11b, 11b are shaft portions of the titanium alloy cylinder 11, 1
1a is the reinforcing ring, 2, 2, and 2 are odd-numbered divided rare earth magnets, 23 and 23 are non-magnetic end plates, and 25 is a non-magnetic metal cylinder. For the non-magnetic metal cylinder 25, a non-magnetic metal material such as an aluminum alloy, a titanium alloy, an austenitic stainless steel, or a high-manganese steel machined member is used.

In this embodiment, the odd-numbered rare-earth magnets 2, 2, 2 and the non-magnetic end plate 23 and the non-magnetic metal cylinder 25 are used.
It is characterized by combining. The manufacturing process is substantially the same as that of the tenth embodiment (FIG. 11).

FIGS. 13A, 13B and 13C show the first embodiment of the present invention.
It is a schematic diagram of a rotor structure (k) showing a second embodiment,
11b, 11b are shaft portions of the titanium alloy cylinder 11, 1
1a is the reinforcing ring, 21 is a ferromagnetic shaft, 5 is an iron core made of a laminated material, 23 and 23 are nonmagnetic end plates, 6 and 6 are iron core grooves, 2 and 2 are rare earth magnets, and 25 is a nonmagnetic metal cylinder. is there. The manufacturing process will be briefly described. (1) Non-magnetic end plate 2
The core 5 made of a laminated material is combined between the ferrules 3 and 23 and press-fitted into the ferromagnetic shaft 21. (2) Rare earth elements are inserted into the wedge-shaped core grooves 6 and 6 provided along the longitudinal direction at the periphery of the core 5. (3) The titanium alloy cylinder 11 was heated to a high temperature of about 300 ° C. to 350 ° C. to apply an axial compressive load to both ends of the shaft portions 11b and 11b. By shrink-fitting the nonmagnetic metal cylinder 25 from the outer periphery of the reinforcing ring 11a in the state, the titanium alloy cylinder 11 divided into two parts is mechanically restrained, and (3) the shaft portions 11b, 11b of the titanium alloy cylinder 11 Both ends are sandwiched between chucks of a rotary jig, and are integrally joined while rotating while slightly applying a compressive load in the axial direction.

Also in this example, since the titanium alloy disk 18 used in each of the above examples is not used, electron beam welding is unnecessary.

FIGS. 14A, 14B and 14C show the first embodiment of the present invention.
It is a schematic diagram of a rotor structure (l) showing a third embodiment,
11b, 11b are shaft portions of the titanium alloy cylinder 11, 1
1a is the reinforcing ring, 5 is an iron core made of a laminated material, 6 and 6 are iron core grooves, 2, 2 are rare earth magnets, and 25 is a non-magnetic metal cylinder. The laminated material of the iron cores 5, 5 is made of a silicon steel plate, for example, 6.5.
% High silicon steel sheets are laminated and used. The manufacturing process is as follows: (1) Insert rare earth magnets 2 and 2 into core grooves 6 and 6 having a wedge-shaped cross section provided along the longitudinal direction at the peripheral edges of iron cores 5 and 5 made of a laminated material and mechanically restrain them. (2) The titanium alloy cylinder 11 is heated to a high temperature of about 300 ° C. to 350 ° C. to apply an axial compressive load to both ends of the shaft portions 11b and 11b. The non-magnetic metal cylinder 2 from the outer periphery of the reinforcing ring 11a
5 is shrink-fitted to mechanically restrain the titanium alloy cylinder 11 divided into two parts. (3) The both ends of the shaft portions 11b and 11b of the titanium alloy cylinder 11 are sandwiched between chucks of a rotary jig, and are axially moved. They are joined together while rotating with a slight compression load applied.

In this example, since the titanium alloy disk 18 and the ferromagnetic shaft 21 are not used, the feature is that electron beam welding is not required and the configuration is simplified.

Next, various modifications of the method of manufacturing a cylindrical member having a different diameter by the "superplastic gas pressure forming method" employed in the present invention will be described. Since the main parts of the apparatus are basically the same as those of the first embodiment shown in FIGS. 1 and 2, the same parts are denoted by the same reference numerals.

FIGS. 15A and 15B are schematic views of a superplastic gas pressure forming apparatus showing a fourteenth embodiment of the present invention, in which a titanium alloy cylinder before and after gas pressure forming, respectively. 11 shows a cross-sectional shape. As main components, 12 and 13 are vertically divided two-piece molds for holding the titanium alloy cylinder 11, 15 is a pipe for supplying high-temperature and high-pressure argon gas, and 16 is a titanium alloy cylinder via the molds 12 and 13. 11 is a heater for heating, 17 is a heat insulating layer, and 8 and 9 are water cooling pipes.

This embodiment is characterized in that a lid member 26 is used in place of the gas storage tank 14 (see FIG. 1) used in the first embodiment.

According to the fourteenth embodiment, after the titanium alloy cylinder 11 is inserted inside the two-part molds 12 and 13,
Both end flange portions 12a, 12b and 13a, 13b are fixed to the flange portion 15a of the pipe 15 for supplying high-pressure argon gas and the flange portion 14a of the gas storage tank 14 by bolting, and the pipe 15 is connected from a large-capacity gas tank (not shown). A high pressure and high temperature argon gas as an inert gas is introduced as a pressure medium, and a predetermined pressure and temperature are applied to the titanium metal cylinder 11 while being heated by the heater 16, thereby obtaining titanium as shown in p. A superplastic gas pressure forming process is applied to the metal cylinder
b, 11b and a rotor outer peripheral reinforcing ring 11a can be formed into a cylindrical shape having a different diameter. Further, by providing the cover member 26, a pressing force is applied not only from the argon gas supply side but also from the cover member 26 side at the time of gas pressure molding, so that a uniform internal pressure is provided in the titanium alloy cylinder 11. Can be.

After performing gas pressure molding on the titanium metal cylinder 11, cooling water is flowed through the water cooling pipes 8 and 9 to form the two-part mold 1.
2, 13 and each flange portion 12a, 12b, 13a, 13
b and the titanium alloy cylinder 11 are cooled.

FIGS. 16A and 16B are schematic views of a superplastic gas pressure forming apparatus showing a fifteenth embodiment of the present invention. The basic structure is the same as that of the first and fourteenth embodiments. For this reason, the same reference numerals are assigned and displayed. In this example, vertically divided two-part molds 12 and 13 for holding a titanium alloy cylinder 11
Is characterized in that a pipe 15 for supplying argon gas is provided on one side and a pipe 15a for supplying argon gas is also provided on the other side of the two-piece molds 12 and 13.

According to the fifteenth embodiment, after the titanium alloy cylinder 11 is inserted and fixed inside the two-part molds 12 and 13, both the pipe 15 and the pipe 15a are removed from the large-capacity gas tank (not shown). By applying a predetermined pressure and temperature to the titanium metal cylinder 11 by introducing a high-temperature and high-pressure argon gas from above, the titanium metal cylinder 11 can be subjected to superplastic gas pressure forming. Therefore, the gas filling rate into the titanium metal cylinder 11 is increased, and a more uniform internal pressure can be applied.

FIGS. 17 (A) and 17 (B) are schematic views of a superplastic gas pressure forming apparatus showing a sixteenth embodiment of the present invention. In this embodiment, the titanium alloy in the first embodiment (see FIG. 1) is used. It is characterized in that, instead of the vertically split two-part molds 12 and 13 for holding the cylinder 11, two horizontally split molds 12c and 13c are provided.

The operation of the sixteenth embodiment is basically the same as that of the first embodiment. In the case where the horizontally split two-part molds 12c and 13c are used, it is necessary to provide the mold with a slight taper.

FIGS. 18A and 18B are schematic views of a superplastic gas pressure forming apparatus showing a seventeenth embodiment of the present invention. In this embodiment, a vertically split two-piece metal holding a titanium alloy cylinder 11 is shown. Type 1
It is characterized in that corrugated grooves 27 are formed in advance on the inner diameter sides of 2, 13.

According to the seventeenth embodiment, after the titanium alloy cylinder 11 is inserted and fixed inside the two-piece molds 12 and 13, a high-temperature and high-pressure argon gas is introduced from the pipe 15 to form the titanium metal cylinder. The bellows 28 made of a titanium alloy can be manufactured by subjecting the cylinder 11 to superplastic gas pressure forming under a predetermined pressure and temperature.

Although the strength of the titanium alloy is not much different from that of the austenitic stainless steel, the elasticity of the bellows 28 obtained in the present embodiment is considerably larger than that of the austenitic stainless steel since the elasticity is about 0.6 times. It is large and has excellent spring properties compared to stainless steel bellows. The bellows 28 is an article without a "seam" which does not depend on the conventional welding method, and is effectively used as a non-magnetic bellows for a vacuum circuit breaker, a vacuum holding case, and the like.

[0079]

As described above in detail, according to the rotor using the titanium alloy according to the present invention and the method for manufacturing the same, an inert gas is introduced into the mold as a pressure medium to form the titanium metal cylinder. By applying a predetermined pressure while heating, the titanium metal cylinder is pressurized from the inside and subjected to superplastic gas pressure forming, and formed into a cylindrical member of different diameter consisting of a shaft part and a reinforcing ring on the outer periphery of the rotor. Can be. Therefore, a step of machining a solid cylindrical cylindrical receiving material into a thick cylindrical titanium alloy cylinder, and a step of circumferentially forming a superplastically processed different-diameter cylindrical member with a reinforcing ring at the center of the rotor portion. Excluding the cutting process, the subsequent cutting process is omitted, which significantly reduces the number of machining steps required to manufacture the rotor, increases the material yield, and improves the effective utilization rate of expensive materials. The effect is obtained.

As a superplastic gas pressure forming method, an inert gas introduction pipe is connected to one side of the mold, and a gas reservoir tank is provided on the other side of the mold, or a lid member is provided on the other side of the mold. As a result, the pressing force is applied not only from the supply side of the inert gas but also from the gas storage tank or the lid member side, and a uniform internal pressure can be provided in the titanium alloy cylinder. Further, by introducing a high-temperature and high-pressure inert gas into the mold from both sides of the mold on one side and the other side,
The gas filling rate into the titanium metal cylinder is increased, and a more uniform internal pressure can be applied.

In the manufacture of the rotor, after cutting into two parts in the circumferential direction at the portion of the rotor outer peripheral reinforcing ring of the different diameter cylindrical member, a titanium alloy disk, a rare earth magnet, a non-magnetic end plate, A ferromagnetic shaft and a non-magnetic metal cylinder are combined and arranged. Shrink fitting is performed in a state where an axial compression load is applied to both ends of the shaft. It is completed by joining together over the circumference or shrink-fitting a non-magnetic metal cylinder from the outer periphery of the reinforcing ring, so the number of parts and assembly man-hours are small, and both the shaft and the reinforcing ring have high specific strength. In addition, the rotor can be reduced in size, higher in performance, and lower in inertia by enabling weight reduction.

Since the obtained rotor is incorporated in a reinforcing ring together with a titanium alloy disk, a rare earth magnet, a non-magnetic end plate, a ferromagnetic shaft and the like, the brittleness of the rare earth magnet is compensated for and the rare earth magnet A rotor that can be used for a high-speed rotating machine or the like can be obtained without lowering the original magnetic characteristics. Therefore, even if the centrifugal force acting on the rotor increases as the speed of the electric motor or the like increases or the capacity increases, the fear that the rare earth magnet is deformed or broken can be greatly reduced.

Therefore, according to the present invention, the man-hour for manufacturing the rotor is significantly reduced, the effective utilization rate of expensive materials is improved, and the brittleness, strength, rigidity, toughness, etc. of the rare-earth magnet are insufficient. And a high-speed and large-capacity motor rotor without deteriorating the magnetic characteristics.

[Brief description of the drawings]

FIG. 1 is a schematic view showing a cross-sectional shape of a titanium alloy cylinder before gas pressure forming according to a first embodiment of the present invention.

FIG. 2 is a schematic diagram showing a cross-sectional shape of a titanium alloy cylinder after pressure molding with an inert gas in the first embodiment.

FIG. 3A is a cross-sectional view of a main part showing a second embodiment, and FIG. 3B is a cross-sectional view taken along line BB of FIG. 3A.

4A is a cross-sectional view of a main part showing a third embodiment, FIG. 4B is a cross-sectional view taken along line BB of FIG. 3A,
FIG. 4C is a cross-sectional view taken along line CC of FIG. 4A.

FIG. 5A is a cross-sectional view of a principal part showing a fourth embodiment, and FIG. 5B is a cross-sectional view taken along line BB of FIG. 5A.

FIG. 6A is a cross-sectional view of a principal part showing a fifth embodiment, and FIG. 6B is a cross-sectional view taken along line BB of FIG. 6A.

7A is a cross-sectional view of a main part showing a sixth embodiment, FIG. 7B is a cross-sectional view taken along line BB of FIG. 7A,
FIG. 7C is a cross-sectional view taken along line CC of FIG. 7A.

8A is a cross-sectional view of a main part showing a seventh embodiment, FIG. 8B is a cross-sectional view taken along line BB of FIG. 8A,
FIG. 8C is a cross-sectional view taken along line CC of FIG. 8A.

9A is a cross-sectional view of a principal part showing an eighth embodiment, FIG. 9B is a cross-sectional view taken along the line BB of FIG. 9A,
FIG. 9C is a cross-sectional view taken along line CC of FIG. 9A.

10A is a sectional view of an essential part showing a ninth embodiment, FIG. 10B is a sectional view taken along the line BB of FIG. 10A, and FIG. Sectional drawing which follows the CC line of 10 (A).

11A is a sectional view of a main part showing a tenth embodiment, FIG. 11B is a sectional view taken along line BB of FIG. 11A, and FIG. Sectional drawing which follows the CC line of 11 (A).

12A is a cross-sectional view of an essential part showing an eleventh embodiment, FIG. 12B is a cross-sectional view taken along the line BB of FIG. 12A, and FIG. Sectional drawing which follows the CC line of 12 (A).

13A is a sectional view of a main part showing a twelfth embodiment, FIG. 13B is a sectional view taken along the line BB of FIG. 13A, and FIG. Sectional drawing which follows the CC line of 13 (A).

14A is a sectional view of a principal part showing a thirteenth embodiment, FIG. 14B is a sectional view taken along the line BB of FIG. 14A, and FIG. Sectional drawing which follows the CC line of 14 (A).

FIG. 15A is a schematic diagram showing a cross-sectional shape of a titanium alloy cylinder before gas pressure forming according to a fourteenth embodiment,
FIG. 15B is a schematic diagram showing a cross-sectional shape of a titanium alloy cylinder after gas pressure molding.

FIG. 16A is a schematic diagram showing a cross-sectional shape of a titanium alloy cylinder before gas pressure forming according to a fifteenth embodiment,
FIG. 16B is a schematic view showing a cross-sectional shape of a titanium alloy cylinder after gas pressure molding.

FIG. 17A is a schematic diagram showing a cross-sectional shape of a titanium alloy cylinder before gas pressure forming according to a sixteenth embodiment,
FIG. 17B is a schematic diagram showing a cross-sectional shape of a titanium alloy cylinder after gas pressure molding.

FIG. 18A is a schematic view showing a cross-sectional shape of a titanium alloy cylinder before gas pressure forming according to a seventeenth embodiment,
FIG. 18B is a schematic diagram showing a cross-sectional shape of a titanium alloy cylinder after gas pressure molding.

FIG. 19: “Ti-4.5Al-3V-2Fe-2M”
7 is a graph showing temperature characteristics of elongation at break and flow stress obtained in a tensile test of an “o” alloy and a “Ti-6Al-4V” alloy.

FIG. 20 is an essential part cross-sectional view showing a schematic structure of a rotor using a conventional rare earth magnet.

FIG. 21 is a sectional view of a main part showing a schematic structure of another rotor using a conventional rare earth magnet.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 ... Shaft 2 ... Rare earth magnet 3 ... Metal cylinder 4 ... Metal disk 5 ... Iron core 6 ... Iron core groove part 8, 9 ... Water cooling piping 11 ... Titanium alloy cylinder 11a ... Reinforcement ring 11b ... Shaft part 12, 13 ... 2 split metal Mold 14 ... Gas storage tank 16 ... Heater 17 ... Heat insulation layer 18 ... Titanium alloy disc 19 ... Electron beam welded part 20 ... Non-magnetic shaft 21 ... Ferromagnetic shaft 21a ... Slotted shaft 22 ... Key 23 ... Non-magnetic end plate 24 … Shaft (made of aluminum die-cast) 25… non-magnetic metal cylinder 26… lid member 27… groove

Claims (23)

[Claims] 1. A titanium alloy thick-walled cylinder is plastically processed by superplastic gas pressure forming into a cylindrical member having a shaft portion and a rotor outer peripheral portion reinforcing ring, and a high-energy product rare earth element is provided in the rotor outer peripheral reinforcing ring. A rotor using a titanium alloy, which has a built-in magnet and iron core material. 2. A titanium alloy thick-walled cylinder is subjected to plastic working by a superplastic gas pressure forming method to a cylindrical member having a shaft portion and a rotor outer peripheral portion reinforcing ring, which has a high energy product. A method for manufacturing a rotor using a titanium alloy, characterized by incorporating a rare earth magnet, an iron core material, and the like. 3. As a superplastic gas pressure forming method, a titanium alloy cylinder is inserted and fixed inside a mold, and a high-temperature and high-pressure inert gas is introduced into the mold while heating the titanium alloy cylinder with a heater. Pressurizing from the inside of the titanium metal cylinder by applying superplastic gas pressure forming to the titanium metal cylinder to form a cylinder having a different diameter comprising a shaft and a rotor outer peripheral reinforcing ring. A method for manufacturing a rotor using a titanium alloy. 4. The titanium metal cylinder is made of “Ti-4.5Al-
The processing conditions for superplastic gas pressure forming in the case of “3V-2Fe-2Mo” alloy include a forming temperature of 780 ° C. ± 50 ° C., a strain rate of 1 × 10 ⁻² / s or less, and an inert gas pressure of 2
The method for manufacturing a rotor using a titanium alloy according to claim 2, wherein the rotor is set to 0 to 120 MPa. 5. The titanium metal cylinder is made of “Ti-6Al-4”.
The processing conditions for the superplastic gas pressing in the case of the “V” alloy include a forming temperature of 880 ° C. ± 50 ° C. and a strain rate of 1 × 10
^-2 / s or less, claim 2 or claim 3 pressure of the inert gas is characterized in that the 20～120MPa 1
14. A method for manufacturing a rotor using the titanium alloy described in the item 6. 6. A cylindrical member formed of a shaft portion and a rotor outer peripheral portion reinforcing ring formed by a superplastic gas pressure forming method is cut into two portions in a circumferential direction at a portion of the reinforcing ring. Rare earth magnets are combined and arranged on both sides centering on a titanium alloy disk, and the different diameter cylindrical members are heated to a high temperature and shrink-fitted with an axial compressive load applied to both ends of the shaft part. The butt of the reinforcing ring and the titanium alloy disc are joined together by electron beam welding while rotating the butt of the reinforcing ring and the titanium alloy disk while rotating with the compressive load applied in the axial direction, without any gap. Features,
A method for manufacturing a rotor using a titanium alloy. 7. The rotor according to claim 6, wherein a rare-earth magnet and a non-magnetic shaft are combined on both sides of the titanium alloy disk in the reinforcing ring. Production method. 8. A cylindrical member formed of a shaft portion and a rotor outer peripheral portion reinforcing ring formed by superplastic gas pressure forming method is cut into two parts in a circumferential direction at a part of the reinforcing ring, and then cut inside the reinforcing ring. The iron core is placed on both sides centering on the titanium alloy disk, and a rare earth magnet is inserted and restrained in the iron core groove provided along the peripheral edge longitudinal direction of this iron core, and the different diameter cylindrical member is heated to a high temperature. Perform shrink-fit with the axial compression load applied to both ends of the shaft, align the butting portions of the reinforcement ring with no gap, and rotate the reinforcement ring while applying the compression load in the axial direction. A method of manufacturing a rotor using a titanium alloy, comprising joining an abutting portion and a titanium alloy disk integrally over an entire circumference by electron beam welding. 9. The method for manufacturing a rotor using a titanium alloy according to claim 8, wherein a two-layer solid shaft is used as an iron core. 10. The method for manufacturing a rotor using a titanium alloy according to claim 8, wherein a bulk material made of a ferromagnetic material such as pure iron, low carbon steel, and low alloy steel is used as the iron core. . 11. The method for producing a rotor using a titanium alloy according to claim 8, wherein a laminated material obtained by laminating silicon steel plates is used as the iron core. 12. A cylindrical member having a shaft portion and a rotor outer peripheral portion reinforcing ring formed by superplastic gas pressure forming is cut into two parts in the circumferential direction at the reinforcing ring portion.
An iron core is pressed into a ferromagnetic shaft centered on a titanium alloy disk in the reinforcing ring, and a rare earth magnet is inserted and restrained in a core groove provided along a peripheral edge longitudinal direction of the iron core, thereby forming a different diameter. The cylindrical member was heated to a high temperature and shrink-fitted in a state where an axial compressive load was applied to both ends of the shaft, and the compressive load was applied in the axial direction after aligning the butting portions of the reinforcing ring with no gap. A method of manufacturing a rotor using a titanium alloy, comprising joining an abutting portion of a reinforcing ring and a titanium alloy disk integrally over the entire circumference by electron beam welding while rotating in a state. 13. A cylindrical member formed of a shaft portion and a rotor outer peripheral portion reinforcing ring formed by a superplastic gas pressure forming method is cut into two parts in a circumferential direction at a portion of the reinforcing ring.
The iron core and the non-magnetic end plate are press-fitted into the ferromagnetic shaft and arranged around the titanium alloy disk in the reinforcing ring, and the rare earth magnet is inserted into the core groove provided along the peripheral edge longitudinal direction of this iron core. Restrain, heat the different diameter cylindrical member to high temperature, shrink fit with axial compression load applied to both ends of the shaft part, fit the butt portion of the reinforcing ring without gap, and then axially A method for manufacturing a rotor using a titanium alloy, comprising joining an abutting portion of a reinforcing ring and a titanium alloy disk integrally over an entire circumference by electron beam welding while rotating while applying a compressive load. 14. The method according to claim 13, wherein a grooved ferromagnetic shaft is used as the ferromagnetic shaft. 15. A ferromagnetic shaft comprising an aluminum die-cast shaft.
A method of manufacturing a rotor using the titanium alloy according to any one of Items 2 and 13. 16. A cylindrical member formed of a shaft portion and a rotor outer peripheral portion reinforcing ring formed by a superplastic gas pressure forming method is cut into two parts in a circumferential direction at a portion of the reinforcing ring,
Magnetic end plates are arranged on both sides centering on the rare earth magnet in the reinforcing ring, and the different diameter cylindrical member is heated to a high temperature, and an axial compressive load is applied to both ends of the shaft portion from the outer periphery of the reinforcing ring portion. A method of manufacturing a rotor using a titanium alloy, wherein a titanium alloy cylinder divided into two parts is mechanically restrained and integrally joined by shrink-fitting a nonmagnetic metal cylinder. 17. The method for manufacturing a rotor using a titanium alloy according to claim 16, wherein an odd number of divided rare earth magnets are arranged in a rotor outer peripheral reinforcing ring. 18. After cutting a cylindrical member formed of a shaft portion and a rotor outer peripheral portion reinforcing ring formed by superplastic gas pressure forming into two parts in a circumferential direction at a portion of the reinforcing ring,
The laminated core is press-fitted into the ferromagnetic shaft and placed in the reinforcing ring, and a rare earth magnet is inserted and restrained in the core groove provided along the longitudinal direction of the periphery of the core, and the cylindrical member having a different diameter is heated to a high temperature. By heating and shrink-fitting the non-magnetic metal cylinder from the outer periphery of the reinforcing ring part while applying an axial compressive load to both ends of the shaft part, the titanium alloy cylinder divided into two parts is mechanically restrained. A method of manufacturing a rotor using a titanium alloy, which comprises integrally joining. 19. The non-magnetic metal cylinder is made of a non-magnetic metal material such as an aluminum alloy, a titanium alloy, an austenitic stainless steel, or a high-manganese steel machined member. A method for manufacturing a rotor using the titanium alloy according to any one of the above items. 20. As a superplastic gas pressure forming method, an inert gas introduction pipe is connected to one side of a mold, a gas reservoir tank is provided on the other side of the mold, and a titanium alloy cylinder is placed inside the mold. By inserting and fixing the titanium alloy cylinder with a heater while introducing a high-temperature and high-pressure inert gas into the mold from an inert gas introduction pipe while heating the titanium alloy cylinder, and performing a pressure treatment from inside the titanium metal cylinder, the titanium A method of manufacturing a rotor using a titanium alloy, wherein a metal cylinder is subjected to superplastic gas pressure forming to form a cylindrical shape having a different diameter comprising a shaft portion and a rotor outer circumferential reinforcing ring. 21. The method for manufacturing a rotor using a titanium alloy according to claim 20, wherein a lid member is provided on the other side of the mold and closed as a superplastic gas pressure molding method. 22. A superplastic gas pressure forming method comprising providing an inert gas introduction pipe on one side and the other side of a mold, and introducing a high-temperature and high-pressure inert gas into the mold from both sides. A method for manufacturing a rotor using the titanium alloy according to claim 20. 23. A corrugated groove is provided on the inner diameter side of the mold,
22. A titanium alloy bellows is formed by introducing a high-temperature and high-pressure argon gas into a titanium alloy cylinder and applying superplastic gas pressure forming at a predetermined pressure and temperature. 23. A method of manufacturing a rotor using the titanium alloy according to any one of items 22.